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Effect Of Some Section Modifications And Protuberances On The Zero Lift Drag Of Delta Wings At Transonic And Supersonic Speeds
Download Effect Of Some Section Modifications And Protuberances On The Zero Lift Drag Of Delta Wings At Transonic And Supersonic Speeds full books in PDF, epub, and Kindle. Read online Effect Of Some Section Modifications And Protuberances On The Zero Lift Drag Of Delta Wings At Transonic And Supersonic Speeds ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effect of Some Section Modifications and Protuberances on the Zero-lift Drag of Delta Wings at Transonic and Supersonic Speeds by : Carl A. Sandahl
Download or read book Effect of Some Section Modifications and Protuberances on the Zero-lift Drag of Delta Wings at Transonic and Supersonic Speeds written by Carl A. Sandahl and published by . This book was released on 1954 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Some Section Modifications and Perturberances on the Zero-lift Drag of Delta Wings at Transonic and Supersonic Speeds by : Carl A. Sandahl
Download or read book Effect of Some Section Modifications and Perturberances on the Zero-lift Drag of Delta Wings at Transonic and Supersonic Speeds written by Carl A. Sandahl and published by . This book was released on 1954 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Index of NACA Technical Publications by : United States. National Advisory Committee for Aeronautics
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1959 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research Abstracts and Reclassification Notice by : United States. National Advisory Committee for Aeronautics
Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 716 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1960 with total page 476 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 by : Robert S. Osborne
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Large-scale Flight Measurements of Zero-lift Drag and Low-lift Drag of 10 Wing-body Configurations at Mach Numbers from 0.8 to 1.6 by : John D. Morrow
Download or read book Large-scale Flight Measurements of Zero-lift Drag and Low-lift Drag of 10 Wing-body Configurations at Mach Numbers from 0.8 to 1.6 written by John D. Morrow and published by . This book was released on 1953 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A New Dimension, Wallops Island Flight Test Range by : Joseph Adams Shortal
Download or read book A New Dimension, Wallops Island Flight Test Range written by Joseph Adams Shortal and published by . This book was released on 1978 with total page 796 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Reduction of Drag Due to Lift at Supersonic Speeds by : Douglas Aircraft Company
Download or read book Reduction of Drag Due to Lift at Supersonic Speeds written by Douglas Aircraft Company and published by . This book was released on 1955 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: $EVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
Book Synopsis Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8 by : H. Herbert Jackson
Download or read book Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8 written by H. Herbert Jackson and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Examples of the Applications of the Transonic and Supersonic Area Rules to the Prediction of Wave Drag by : Robert L. Nelson
Download or read book Some Examples of the Applications of the Transonic and Supersonic Area Rules to the Prediction of Wave Drag written by Robert L. Nelson and published by . This book was released on 1960 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Drag Due to Lift at Mach Numbers Up to 2.0 by : Edward C. Polhamus
Download or read book Drag Due to Lift at Mach Numbers Up to 2.0 written by Edward C. Polhamus and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Two Leading-edge Modifications on the Aerodynamic Characteristics of a Thin Low-aspect-ratio Delta Wing at Transonic Speeds by : John P. Mugler
Download or read book Effects of Two Leading-edge Modifications on the Aerodynamic Characteristics of a Thin Low-aspect-ratio Delta Wing at Transonic Speeds written by John P. Mugler and published by . This book was released on 1956 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 8-foot transonic tunnel to determine the aerodynamic characteristics of a thin 60 degree delta wing with two leading-edge modifications (conical leading-edge camber and leading-edge droop) in combination with bodies with and without body indentation in accordance with the transonic-area-rule concept. The tests covered a Mach number range from 060 to 1.15 and an angle-of-attack range from -4 to 20 degrees at a Reynolds number of about 3,000,000 based on the wing mean aerodynamic chord. The wing had an aspect ratio of 2.31, a taper ratio of 0, and, without modifications, had NACA 65A003 airfoil sections parallel to the model plane of symmetry.
Book Synopsis Effects of Some Leading-edge Modifications, Section and Plan-form Variations, and Vertical Position on Low-lift Wing Drag at Transonic and Supersonic Speeds by : Clement J. Welsh
Download or read book Effects of Some Leading-edge Modifications, Section and Plan-form Variations, and Vertical Position on Low-lift Wing Drag at Transonic and Supersonic Speeds written by Clement J. Welsh and published by . This book was released on 1955 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Free-flight rocket-propelled model tests have been made to determine the effect of some wing geometry variables on low lift drag at Mach numbers from approximately 0.6 to 2.1. The pertinent results relate to 4- to 7-percent-thick 45 degree sweptback wings. At supersonic speeds, the wing drag was higher with the NACA 2-006 airfoil sections than with the NACA 65A006 airfoil sections particularly at the higher test Mach numbers where it was over 40 percent higher. Drooping the forward 20 percent of the wing 6 degrees increased the wing drag coefficient as much as 30 percent at supersonic speeds. Moving the wing vertically from the fuselage center line to the top of the fuselage increased the configuration drag substantially at supersonic speeds.
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by :
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by and published by . This book was released on 1954 with total page 818 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-wedge Sections with the Maximum Thickness at 0.18 Chord by : Mitchel H. Bertram
Download or read book Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-wedge Sections with the Maximum Thickness at 0.18 Chord written by Mitchel H. Bertram and published by . This book was released on 1954 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section has been conducted at the Langley 11-inch hypersonic tunnel. These wings had a maximum thickness of 8 percent of the chord located at the 18-percent-chord point. For the wings tested at a Mach number of 6.9, the semiapex angle was varied from 5 to 30 degrees and the wings were tested over a range of angle of attack from 0 to 28 degrees and Reynolds numbers in the range of 800,000 to 3,600,000 based on root chord. In addition, pertinent results from tests at Mach number as low as 1.62 have been utilized. The shock-expansion theory and the Newtonian impact theory have been used to analyze the effects of changes made in the various parameters investigated.
